Igniter for gas turbine engine

ABSTRACT

There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.

TECHNICAL FIELD

The application relates generally to gas turbine engines and, moreparticularly, to igniters used for gas turbine engines.

BACKGROUND OF THE ART

Spark plugs are commonly used to ignite a mixture of air and fuel in acombustor of gas turbine engines. However, spark plugs for example havedrawbacks. For instance, the spark plugs have been known to achieve lessthan full reliability in conditions such as when wet by exposure tocondensation or washing fluid, or when the fuel and the engine are verycold. Cost is also a factor. There is always room for improvement.

SUMMARY

In one aspect, there is provided an igniter for a gas turbine enginecomprising: a base including a securing assembly configured to bematingly connected to a casing of the gas turbine engine, a glow plugheater rod, the glow plug heater rod extending from the base along anaxis and terminating in a rod end, a flow impeding member extendingalong the axis and having a distal end spaced from the base andextending axially relative to the axis beyond the rod end, the flowimpeding member sized and configured such that the distal end extendsinto a combustion chamber of the gas turbine engine upon the baseconnected to the casing.

In another aspect, there is provided a method of operating a gas turbineengine, the method comprising: circulating compressed gas in acompressed gas passage between a casing and a combustion chamber liner,the combustion chamber liner delimiting a combustion chamber, exposing aheating section of a glow plug heater rod to a mixture of air and fuelin the combustion chamber via an aperture in the combustion chamberliner; forming a curtain of cooling air along an inner surface of saidcombustion chamber liner; and blocking said curtain of cooling airaround an end of said glow plug heater rod, thereby providing a pocketof lower velocity around said end.

In yet another aspect, there is provided a gas turbine enginecomprising: a casing; a combustor liner provided inside the casing andenclosing a combustion chamber; an igniter having a base connected tothe casing, a glow plug heater rod extending from the base along an axisand terminating in a rod end, a flow impeding member extendingcircumferentially around the heater rod along at least a portion of alength of the glow plug heater rod, the flow impeding member protrudingaxially into the combustion chamber.

DESCRIPTION OF THE DRAWINGS

Reference is now made to the accompanying figures in which:

FIG. 1 is a schematic cross-sectional view of a gas turbine engine;

FIG. 2 is an oblique view of an igniter in accordance with oneembodiment;

FIG. 3 is a cross-sectional view of the igniter of FIG. 2, taken along alongitudinally-oriented plane, shown in an environment of use;

FIG. 4 is a cross-sectional view of an igniter in accordance withanother embodiment;

FIG. 5 is a bottom view of the igniter of FIG. 4;

FIG. 6 is a cross-sectional view of an igniter in accordance withanother embodiment;

FIG. 7 is a bottom view of the igniter of FIG. 6;

FIG. 8 is a view of an igniter in accordance with another embodiment;

FIG. 9 is a view of an igniter in accordance with another embodiment;

FIG. 10 is a schematic tridimensional view of an igniter in accordancewith another embodiment;

FIG. 11 is a of an igniter in accordance with another embodiment;

FIG. 12 is an oblique view of an igniter in accordance with anotherembodiment;

FIG. 13 is an oblique view of an igniter in accordance with anotherembodiment;

FIG. 14 is a partial, schematic, cross-sectional view of an igniter inaccordance with another embodiment;

FIG. 15 is a partial, schematic, cross-sectional view of an igniter inaccordance with another embodiment;

FIG. 16 is a partial, schematic cross-sectional view of an igniter inaccordance with another embodiment;

FIG. 17 is an oblique view of an igniter in accordance with anotherembodiment;

FIG. 18 is an oblique view of a swirler which can be used as part of theigniter of FIG. 17;

FIG. 19 is a schematic cross-sectional view of an igniter in accordancewith another embodiment;

FIG. 20 is a schematic cross-sectional view of an igniter in accordancewith another embodiment;

FIG. 21 is a schematic cross-sectional view of an igniter in accordancewith another embodiment;

FIG. 22 is a schematic bottom view of an igniter in accordance withanother embodiment;

FIG. 22a is a schematic cross-sectional view of the igniter of FIG. 22;

FIG. 23 is a schematic bottom view of an igniter in accordance withanother embodiment;

FIG. 23a is a schematic cross-sectional view of the igniter of FIG. 23;

FIG. 24 is a partial, schematic cross-sectional view of a heater rod ofa glow plug in accordance with another embodiment;

FIG. 25 is a partial, schematic, cross-sectional view of an igniter inaccordance with another embodiment; and

FIG. 26 is a partial, schematic cross-sectional view of a variation ofthe igniter of FIG. 25.

DETAILED DESCRIPTION

FIG. 1 illustrates a gas turbine engine 10 of a type preferably providedfor use in subsonic flight, generally comprising in serial flowcommunication a fan 12 through which ambient air is propelled, acompressor section 14 for pressurizing the air, a combustor 16 in whichthe compressed air is mixed with fuel and ignited for generating anannular stream of hot combustion gases, and a turbine section 18 forextracting energy from the combustion gases. The fan 12, the compressorsection 14, and the turbine section 18 rotate about a central axis 11.

In this embodiment, the gas turbine engine includes an engine casing 25that is disposed radially outwardly of the combustor 16 relative to thecentral axis 11. The combustor 16 has a combustor liner 16 a thatencloses a combustion chamber 16 b. The combustor liner 16 a can formpart of the engine casing 25 and not rotate with the rotors. Thecombustor liner 16 a defines at least one igniter liner aperture 16 cfor receiving at least one igniter 20 (FIG. 2), which is used forigniting a mixture of compressed air from the compressor section 14 andfuel injected by fuel injectors 22.

The engine casing 25 can also have one or more igniter apertures 25 a,configured to receive the igniter 20 therein. As shown in greater detailin the example presented in FIG. 3, the igniter aperture 25 a can bealigned with the igniter liner aperture 16 c of the combustor liner 16a. In one embodiment, an axis of the igniter aperture 25 a is coincidentwith an axis of the igniter liner aperture 16 c. The igniter aperture 25a and the igniter liner aperture 16 c can be said to form, collectively,an igniter socket. This alignment can allow an igniter to be received byboth of the igniter liner aperture 16 c and the igniter aperture 25 a toreach the combustion chamber 16 b of the combustor 16. In gas turbineengine 10, the igniter socket has a female thread designed to receive amating male thread of a spark plug. Accordingly, a peripheral wall 25 bof the igniter aperture 25 a may include a threads 25 c to be engaged bythe igniter 20.

As will be described in greater detail below, a glow plug can be used toignite fuel in a gas turbine engine and in some cases, suchglow-plug-based igniters can have advantages over spark plugs. Thefollowing paragraphs present various embodiments of glow-plug-basedigniters for use in a gas turbine engine setting, and a discussion aboutvarious elements which may have to be taken into consideration whenretrofitting a glow-plug-based igniter into a spark plug aperture of agas turbine engine.

More specifically some igniters having a heater in the form of anexposed coil shaped resistors have been referred to as “glow plugs” inthe past. In newer glow plug designs, the heater is typicallyencapsulated in a protective shell and the resulting assembly isreferred to as a heater rod. Spark plugs ignite a mixture of air andfuel by generating a spark whereas glow plugs ignite such a mixture ofair and fuel by having a tip section heated at a temperature above thefuel ignition temperature. At such elevated temperatures, the tipsection “glows”, which led to the use of the familiar expression “glowplug”. A typical heater rod can have a surface made of non-oxidizingmaterial that can withstand temperatures above 1000 degrees Celsius,which can impede carbon formation.

In the embodiment illustrated, the gas turbine engine 10 was initiallydesigned for using a specific model of spark plugs as the igniters. Theigniter presented in FIG. 2 includes a heater rod, and was designed tobe used instead of the spark plugs.

There can be dimensional issues to consider in using a heater rod-basedigniter in a spark plug socket. Indeed, off-the-shelf glow plugs can besmaller in diameter than the spark plugs designed for the specific gasturbine engine 10. It can be desired to control the depth of the heatingtip of the heater rod. Moreover, it may be desired to provide theigniter with some additional feature or features, which may not beintegrated with the off the shelf glow plugs, to allow them to be bettersuited for the gas turbine engine environment.

One avenue is to design glow plugs specifically for the intended use andcontext, which can include providing a body having suitable featureswhich an off-the shelf glow-plug does not have. Another alternative isto design an adapter to a) fit a spark plug aperture, b) receive anoff-the shelf glow plug and c) provide any additional feature useful inadapting the off-the-shelf glow plug to the specific gas turbine engineenvironment. In several of the embodiments described and illustrated,the avenue of using an igniter consisting of an off-the-shelf glowplug+adapter was preferred over the avenue of providing a new glow plugdesign, mostly because it was easier to design an adapter for anexisting glow plug design than to design and producing a specific, newglow plug design specifically adapted to the application. Nonetheless,specific glow plug designs used without adapters can be preferred insome embodiments, and will be discussed further below.

In the embodiment shown in FIG. 3, the igniter liner aperture 16 c andthe igniter aperture 25 a correspond to a spark plug socket PSconfigured for receiving therein a spark plug. A flow F′ of compressedair exits the compressor section 14 and is fed in an annular spacing 51,also referred to as a compressed gas passage, defined radially betweenthe combustor liner 16 a and the engine casing 25 relative to thecentral axis 11. The combustor liner 16 a can have a plurality ofapertures (not shown) configured for allowing the flow F′ of compressedair to enter the combustion chamber 16 b to be mixed with fuel andignited.

Referring to FIGS. 2-3, the igniter 20 includes a glow plug that isgenerally shown at 24. The disclosed glow plug 24 is of a “pencil-type”,and has a heater rod having a protective shell encapsulating a heater.The heater can be a coiled resistive element. As shown, the glow plug 24extends along an axis A and has a body 24 a and a heater rod 24 bprotruding from the body 24 a along the axis A. As shown, the heater rod24 b extends across the spacing S1. In the depicted embodiment, theheater rod 24 b has a ceramic portion which includes the “heaterportion” of the glow plug 24 that becomes hot and “glows” to ignite themixture of air and fuel. Various types of heater rods exist, in sometypes of heater rods, the heater rod 24 b of the glow plug 24 may bemade of a metallic material, in some other types, the glow plug heaterrod 24 b may be covered by a metallic material, such as Inconel™. Theglow plug body 24 a includes a main section 24 c and an intermediatesection 24 d. The intermediate section 24 d is located axially betweenthe main section 24 c and the heater rod 24 b relative to the axis A. Ametal to ceramic junction J may be located at an intersection of theintermediate section 24 d and the heater rod 24 b. As shown, a diameterof the intermediate section 24 d is less than that of the main section24 c and greater than a diameter of the heater rod 24 b. The glow plug24 includes connection means 24 e, which can include a positive and anegative connection terminals, configured to be electrically connectedto a power source. The body 24 a of the glow plug 24 includes a threadedportion 24 f for securing the glow plug 24 to a structural element ofthe gas turbine engine 10 that may be, for instance, the threads 25 c ofthe peripheral wall 25 b of the igniter aperture 25 a of the enginecasing 25.

The glow plug 24 has a heater located inside the heater rod 24 b forheating the heater rod 24. In the embodiment shown, the heater is aheating coil 24 i. Ceramic powder may be provided around the coil 24 ito fill a gap between the coil 24 i and an external shell of the heaterrod 24 b. The heater rod 24 b has a tip section 24 h that extends froman end 24 g of the heater rod toward the body 24 a of the glow plug 24.A length of the tip section 24 h is less than that of the heater rod 24b. The tip section 24 h is also referred to as a heating section of theglow plug 24 as it is that section that “glows” for igniting the mixtureof air and fuel.

The heating section 24 h is typically the portion of the heater rod 24 bthat reaches temperature above 400 degrees Celsius in operation. Theheating section 24 h may reach a temperature of about 1100 degreesCelsius along a length of about 2 mm extending from the end 24 g of theheater rod 24 b, and can be said to extend axially along a portion ofthe length of the heater rod, between the axial positions of the twoopposite ends of the heater.

The combustor liner 16 a has a collar 16 d which surrounds a wholeperiphery/circumference of the igniter liner aperture 16 c. The collar16 d and the combustor liner 16 a may be monolithic, e.g. via machiningfrom a single component, or otherwise integral to one another, e.g. viasoldering. The collar 16 d extends from the combustor liner 16 a towardthe engine casing 25 and within an annular spacing S definedtherebetween. The collar 16 d is configured for receiving a portion ofthe igniter 20

Still referring to FIGS. 2 and 3, in this embodiment, the igniter 20includes an off-the-shelf glow plug 24 and a gas turbine engine adaptor30, referred to hereinbelow simply as an adaptor 30. As discussed above,a primary feature of the adaptor 30 can be to allow to fit anoff-the-shelf glow plug to the female threads which were designed for aspark plug. However, the adaptor can also have one or more featuresproviding additional functionality.

Indeed, in FIGS. 2 and 3, for instance, the adaptor 30 is also used tofill a gap that might otherwise exist between the peripheral wall 25 bof the igniter aperture 25 a of the engine casing 25 and the glow plug24. A sealing engagement may be created between the adaptor 30, morespecifically its outer surface 30 f where it is threaded, and theigniter aperture 25 a that may be correspondingly threaded.

In this embodiment, the adaptor 30 is hollow and defines a cavity 30 aor socket for receiving therein the glow plug 24. An inner surface 30 bof the adaptor 30 may have a threaded portion 30 c configured for beingengaged by threads of the correspondingly threaded portion 24 f of thebody 24 a of the glow plug 24. Other means of securing the adaptor 30 tothe body 24 a of the glow plug 24 may be used without departing from thescope of the present disclosure. In a particular embodiment, a glow plugmay have a body that is tailored to the igniter aperture 25 a of theengine casing 25 or combustor liner 16 d and may not require the adaptor30. Stated otherwise, the glow plug 24 and the adaptor 30 may bemonolithic.

In the embodiment shown, the inner surface 30 b of the adaptor 30defines a constriction 30 h that creates an abutment surface configuredto be in contact with an end of the main section 24 c of the body 24 aof the glow plug 24. The abutment of the glow plug against the innersurface 30 b of the adaptor and at the constriction 30 h may limitmovements relative to the adaptor 30 of the glow plug 24 along its axisA and toward the combustion chamber 16 b.

In the embodiment shown, the adaptor 30 has a first section, alsoreferred to as a casing portion, 30 d and a second section 30 e that areboth annular and define portions of the adaptor conduit 30 a forreceiving the glow plug 24. The second section 30 e includes a securingmechanism, or assembly, SM configured to be matingly connected to thecasing 25 of the gas turbine engine 10. At an outer surface 30 f of theadaptor 30, the first section 30 d has a diameter greater than that ofthe second section 30 e to create an abutment surface 30 g that contactsan outer side of the engine casing 25. In other words, the abutmentsurface 30 g is defined by a shoulder 30 g′ of the adaptor 30. Thesecond section 30 e extends axially relative to the axis A from thefirst section 30 d toward an end of the adaptor 30 and is configured tobe received within the igniter aperture 25 a defined through the enginecasing 25 and through the igniter liner aperture 16 c of the combustorliner 16 a. More specifically, the second section 30 e of the adaptor 30has a threaded section 30 l that is configured to engage the threadedsection 25 c of the peripheral wall 25 b of the igniter aperture 25 a.

The portion of the igniter which is designed to be secured to theigniter aperture 25 a can be referred to as the base, independently ofwhether the igniter is a specific, integral, glow plug design or of the“off-the-shelf glowplug”+adaptor type.

In the embodiment shown, rings also referred to as spacers 29 arelocated between the abutment surface 30 g of the base and the enginecasing 25 for adjusting a depth of penetration of the adaptor in thespacing 51. In other words, either a thickness of the rings 29 along theaxis A and/or a number of the rings 29 may be varied to change the depthof penetration of the adaptor, and hence of the end 24 g of the heaterrod 24 b within the combustion chamber. These spacers 29 were used forexperimental purposes, allowing to easily test different depths of theigniter into the combustion chamber, and will likely be omitted from anindustrial production of igniters (or adaptors), the industrialproduction being specifically designed to have an optimal distancebetween the shoulder engagement and the heater rod tip.

A challenge can arise in relation to the amount of fuel which will beexposed to the heating section of the heater rod, with the objective ofreaching auto-ignition, and flame sustenance conditions.

Another challenge can stem from the body 24 a of the glow plug 24, morespecifically its inter mediate section 24 d (which can be a metal shellportion leading to a ceramic shell portion for instance), being lesstolerant to high temperatures than the tip, and may need to be kept to atemperature that is substantially below the tip temperature and below atemperature inside the combustion chamber 16 b of the combustor 16.

Referring to FIG. 3, the igniter includes a sleeve 32. The sleeve 32 maybe connected to the base B independently of a structure of the gasturbine engine and protruding along the axis A from the base B towardthe rod end 24 g. The sleeve 32 is disposed around the glow plug 24. Thesleeve member 32 has an outer surface 32 a that faces away from the glowplug 24 and an inner surface 32 b that faces the glow plug 24. In theembodiment shown, the sleeve 32 is connected to an adaptor 30. Morespecifically, the second section 30 e of the adaptor 30 defines amechanism 30 j for holding the sleeve 32. In the depicted embodiment,the mechanism 30 j includes a threaded section 30 k of the adaptor 30.The sleeve outer surface 32 a defines a threaded section 32 d that isconfigured to cooperate with the threaded section 30 k of the adaptor 30to limit axial movements of the sleeve 32 with respect to the adaptor 30relative to the axis A. This was provided for test purposes, to allow toeasily test various sleeve designs, and in an industrial production, thesleeve can be integral to the base, for instance. In a particularembodiment, the sleeve 32 is axisymmetric around the axis A, and extendsalong a full circumference of the heater rod, but in alternateembodiments, the sleeve may extend only partially circumferentiallyaround the heater rod or may intermittently extend circumferentiallyaround the heater rod (e.g. be crenellated), for instance.

The sleeve can offer one or more of the following additionalfunctionalities:

a) shielding the heater rod from the circulation of compressed gasbetween the combustion chamber liner and the gas turbine engine casing,

b) forming a constriction in a gap between the sleeve and the heater rodto impede combustion heat from accessing the metal-to-ceramic joint J,

c) fully or partially occupying a gap between which could otherwise bepresent between the combustion chamber liner and the igniter, andthereby impeding flow of compressed gas directly across the combustionliner aperture which could otherwise be detrimental to ignition or flamesustenance conditions,

to name a few examples.

As discussed above, the structure which is used to provide suchadditional functionality to the heater rod can be structurally connectedto the base of the igniter, i.e. the portion of the igniter which issecured to the engine casing. To this end, the structure can be a) i)integrated to an adaptor designed to receive an off-the-shelf glow plug,or ii) be included in the design of a new glow plug design specificallyadapted to these conditions, in which case it can be integral to theglow plug body. However, it will be understood that alternately suchstructure can b) form part of an adaptor member, distinct from the glowplug itself, which is designed to be secured to the combustion chamberliner, for instance, or even c) secured to the heater rod, such as bysoldering or any suitable alternate form of securing. It will beunderstood that other structures providing other possibilities of addedfunctionalities are described below, and that such other structures canbe integrated to the igniter in accordance with either one of theoptions a)i), a)ii), b) or c) above.

In the embodiment shown, the sleeve 32 provides the added functionalityof defining a fuel receiver R that can have a surface designed to bewetted by fuel, in a manner to favor ignition of the by the heater rod24 b. As illustrated in FIG. 3, the sleeve also forms an annularspacing, or annular gap G that circumferentially extends a fullcircumference around the heater rod 24 b. The annular spacing can bedesigned in a manner to provide a pocket area of gaseous fuel and airmixture around the hot tip of the glow plug where the gas velocity islimited, to favor ignition and flame sustenance conditions.

In a particular embodiment, the sleeve 32 may be configured to protectthe heater rod 24 b from the hot compressed air that circulates in thespacing S1 (FIG. 1) and may limit fluid communication from thecombustion chamber 16 b enclosed by the combustor liner 16 c toward thebase B of the igniter 20. In the embodiment shown, the sleeve 32 has asubstantially cylindrical shape. It is understood that other shapes arecontemplated. In a particular embodiment, the sleeve can form aconstriction, axially upward from the annular spacing forming the pocketarea, to protect the plug intermediate section 24 d from excessivetemperature due to elevated air temperatures in the spacing S1immediately after engine shutdown when there is no airflow through theengine.

In a particular embodiment, the fuel receiver R is an open cellstructure, such as a porous media. In a particular embodiment, adistance along the axis between the rod end and the fuel receiverportion located closest to the rod end is less or equal to two times alength of the heating section. In a particular embodiment, the distanceis less or equal to one and a half times the length of the heatingsection, preferably corresponds to the length of the heating section,preferably to about half the lend of the heating section, preferably toabout a quarter of the length of the heating section. Such otherembodiments are discussed further below.

In the embodiment shown, a threaded insert 132 is received in a cavity30 i defined within the base. As shown in FIG. 3, once this threadedinsert is received within the cavity 30 i, a portion of the cavity 30 iremains free of the threaded insert.

In a particular embodiment, the cavity 30 i collects liquid fuel andfuel mist, such that when ignition occurs, said fuel is vaporized and isthereby pushed away from the sleeve 32 and adaptor 30 towards an area ofcombustion in the combustion chamber 16 b. This might lead to increasedcombustion near the ignitor 20 and potentially resulting in a jet offlame away from the ignitor 20 and towards the combustion chamber 16 band a spray generated by the fuel injectors 22 (FIG. 1).

The sleeve 32 may be slidingly received within the collar 16 d. Anexternal diameter of the sleeve 32 may be configured to correspond to aninternal diameter of the collar 16 d to limit the flow F′ of compressedair from entering the combustion chamber 16 b via a gap between thesleeve 32 and the collar 16 d. Stated otherwise, the outer surface 32 aof the sleeve 32 may be in abutment with an inner surface of the collar16 d. The sleeve 32 is discussed in more detail below.

In the embodiment shown, the sleeve 32 is slidingly received within thecollar 16 d of the combustor liner 16 a. The outer surface 32 a of thesleeve 32 may be in abutment against an inner surface of the collar 16d. The engagement of the sleeve 32 and the collar 16 d may be a sealingengagement that might impede fluid flow communication between thecombustion chamber 16 b and the spacing S1 via the collar 16 d. Thesealing engagement might avoid the combustion gases to leak from thecombustion chamber 16 b toward the spacing S1 between the engine casing25 and the combustor liner 16 a.

The sleeve 32 forms a radial, or annular gap G that circumferentiallyextends around a full circumference of the heater rod 24 b in thisembodiment, and more particularly around the tip section 24 h of theglow plug 24. The radial gap G extends radially from the heater rod 24 bto at most the outer surface 32 a of the sleeve 32 relative to the axisA. In a particular embodiment, a depth of the radial gap G taken alongthe axis A varies from zero to seven times a diameter of the heater rod24 b of the glow plug 24. In a particular embodiment, the depth of theradial gap G taken along the axis A is equal to about a length of aportion of the heater rod 24 b that is heated. In a particularembodiment, a value of the length of the portion of the heater rod 24 bthat is heated is approximately equal to a value of the diameter of theheater rod 24 b.

In the embodiment shown, a flow circulation area F is located near theheater rod 24 b. The end 24 g of the heater rod 24 b is positioned inthe flow circulation area F. In the embodiment shown, the flowcirculation area F is defined in part by the sleeve 32. A constrictedarea C extends radially relative to the axis A between the sleeve innersurface 32 b and the heater rod 24 b. The constricted area C is locatedaxially between the flow circulation area F and the body 24 a of theplug 24. The constricted area C is designed to have a smallertransversal cross-sectional area than the cross-sectional area of theflow circulation area F. The transversal cross-sectional area is takenon a plane normal to the glow plug axis A. The annular gap G is fluidlyconnected to the fluid flow circulating area F.

In the embodiment shown, an axial position, relative to the axis A, ofan end 24 g of the glow plug heater rod 24 b corresponds to that of adistal end 32 c of the sleeve 32 that is located inside the chamber 16b. In the embodiment shown, the cross-sectional area of the conduitdecreases from a proximal end of the sleeve 432 to the constriction C.

In the depicted embodiment, the constricted area C is an annular gapthat circumferentially and continuously extends all around the glow plugheater rod 24 b in this embodiment. In the embodiment shown, theconstricted area is axially offset from the tip section 24 h of theheater rod 24 b relative to the axis A of the glow plug 24. As shown,the sleeve inner surface 32 b at both of the flow circulation area F andthe constricted area C is cylindrical and a diameter of the sleeve innersurface 32 b at the flow circulation area F is greater than that at theconstricted area C. In the embodiment shown, a diameter of the heaterrod 24 b of the glow plug 24 is slightly less than that of the innersurface 32 b of the glow plug 24 at the constricted area C to allow formanufacturing tolerances of the diameter D1 of the heater rod 24 b ofthe glow plug 24 and other tolerances, which can be added together, suchas concentricity of a surface of the heater rod 24 b of the glow plug 24relative to the axis A, concentricity of the constriction 30 h relativeto the inner threaded portion of the adaptor 30.

In a particular embodiment, the sleeve 32 allows a sufficient quantityof the mixture of air and fuel to enter the flow circulation area F tobe ignited and, at the same time, protect the glow plug body 24 d fromthe very hot combustion gases within the combustion chamber. In aparticular embodiment, the constricted area C impedes the hot combustiongases to flow toward the body 24 a of the glow plug 24 therebyprotecting the body 24 a of the glow plug 24 against these gases. Morespecifically, and in accordance with a particular embodiment, theconstricted area C reduces the heat transferred to the glow plug bodywhen air temperature is very high due to flames or heat soak-backeffects after start abort or shutdown.

In the embodiment shown, the end 24 g of the heater rod 24 b is axiallyaligned, relative to the axis A, with the igniter liner aperture 16 c.Stated otherwise, the end 24 g is intersected by a projection of thecombustor liner 16 a.

Still referring to FIG. 3, the igniter includes a metal portion M thatis located closes to the heating section 24 h of the heater rod 24 b. Inthe embodiment shown, the metal portion corresponds to the inner surface32 b of the sleeve 32 at the constricted area C. As shown, the heatingsection 24 h protrudes beyond the metal portion. In other words, anentirety of the heating section is axially spaced apart from the metalportion. In a particular embodiment, a distance taken along the axis Afrom the end 24 g of the heater rod 24 g to the metal portion is less orequal to two times a length along the axis A of the heating section 24h. In a particular embodiment, the distance taken along the axis A fromthe end 24 g of the heater rod 24 g to the metal portion is less orequal to one and a half time the length of the heating section 24 htaken along the axis A. In a particular embodiment, the distance takenalong the axis A from the end 24 g of the heater rod 24 g to the metalportion corresponds to the length of the heating section 24 h takenalong the axis A. In a particular embodiment, the distance taken alongthe axis A from the end 24 g of the heater rod 24 g to the metal portionis about half the length of the heating section 24 h taken along theaxis A.

In the embodiment shown, the end 24 g of the heater rod 24 b is locatedinside the combustion chamber 16 b. That is, the end 24 g traverses aprojection 16 a′ of the combustor liner 16 a; the projectioncorresponding to where the combustion liner 16 a would be if the igniterliner aperture 16 c were not present. The projection 16 a′ may bedefined by an interpolation of the combustor liner 16 a to fill theigniter liner aperture 16 c. When seen in a cross-section taken along aplane containing the central axis 11 of the gas turbine engine 10 (asshown on FIG. 3), the projection 16 a′ follows the peripheral wall ofthe igniter liner aperture 16 c. In a particular embodiment, the end 24g of the heater rod 24 b is axially aligned relative to the axis A withthe projection 16 a′.

Many possible embodiments for the sleeve are described herein.Nonetheless, it should be understood that still other variations arepossible without departing from the scope of the present disclosure.

Referring now to FIG. 4, another embodiment of a sleeve is generallyshown at 132 with the adaptor 30 and the glow plug 24 that may beidentical to those shown in FIG. 3.

Referring now to FIGS. 4 and 5, the sleeve 132 defines fins 132 e thatextend axially from bases 132 f to free tips 132 g thereof and radiallyfrom the sleeve inner surface 132 b to the sleeve outer surface 132 a.In the embodiment shown, the fins 132 e are circumferentiallyinterspaced around the axis A and are at equal distance from oneanother. The fins 132 e may be non-uniformly distributed around the axisA such that a distance along a circumferential direction relative to theaxis A and between two adjacent ones of the fins 132 e may vary alongthe circumference of the sleeve 132. The constricted area C is locatedat the bases 132 f of the fins 132 e. In other words, the flowcirculation area F axially starts where the fins 132 e starts andextends radially from the glow plug heater rod 24 b to the sleeve outersurface 132 a via spacing S2 between each of two consecutive ones of thefins 132 e. The constricted area C as shown is substantially from theheating section 24 h, but it can be located close to or in the heatingsection 24 h. The fins may extend intermittently around a fullcircumference of the heater rod 24 b. The sleeve including the fins neednot be axisymmetric. In a particular embodiment, the fins form part ofthe liner portion, also referred to as the collar 16 d.

An axisymmetric design can be preferred in the context where the igniteris to be secured to the gas turbine engine by a threaded engagementconcentric to the heater rod axis, but in certain cases, such as if thecircumferential orientation of the igniter relative to the socket in thegas turbine engine is known, a non-axisymettric design can be preferredto adapt to the specific features of the environment, such as knownposition of incoming fuel mist, known position of heating air, knownlocal orientation of gravity, etc. Accordingly, in one embodiment, thefins can extend intermittently around a full circumference of the heaterrod, whereas in another embodiment, the fins can extend only in one ormore portions, e.g. arcs, of the full circumference of the heater rod.

The sleeve 132 includes a surface from which the fins 132 e protrudes;the surface containing the bases 132 f of the fins 132 e and extendsfrom the inner surface 132 b to the outer surface 132 a. In theembodiment shown, the surface from which the fins 132 e protrude is notflat and is sloped such that a distance from the bases 132 f of the fins132 e to the end 24 g of the heater rod 24 b taken along the axis Adecreases from the inner surface 132 b to the outer surface 132 a. Thesurface from which the fins 132 e protrude may be alternatively flat.Other configurations are contemplated without departing from the scopeof the present disclosure.

The sleeve 132 extends partially around the heater rod 24 b as the fins132 e are circumferentially distributed all around the heater rod 24 b.In other words, in this embodiment the sleeve 132 does not continuouslyextends along a full circumference as gaps are present between twoadjacent ones of the fins 132 e.

In the embodiment shown in FIGS. 4 and 5, the sleeve 132 includes eightfins 132 e. In a particular embodiment, more or less than eight fins maybe used. More specifically, twelve fins may be used. In a particularembodiment, a thickness T1 and a number of fins 132 e, and the spacebetween the fins 132 e which allows the entry of fuel/air mixture,affect ignition performance. In a particular embodiment, a minimum valuefor the thickness T1 of the fins 132 e is about 0.04 to 0.06. In aparticular embodiment, the thickness T1 of the fins 132 e is about 0.01inch, preferably 0.02 inch.

The fins 132 e may be straight as illustrated on FIG. 4 or may be definean “S-shape” or curved shape in a radial direction and/or an axialdirection relative to the axis A. The fins 132 e may extend in acircumferential direction relative to the axis such that they wraparound the heater rod 24 b. Other configurations are contemplatedwithout departing from the scope of the present disclosure.

In a particular embodiment, the fins 132 e, and more particularly thespacing S2 between the fins 132 e promote an exposure of the heater rod24 b to the mixture of air and fuel. This might help in igniting saidmixture. In a particular embodiment, sections of the circumference ofthe inner surface 132 b of the sleeve 32 where the fins 132 e arepresent amount to at least half of a full circumference of said innersurface 132 b.

As shown, the end 24 g of the glow plug heater rod 24 b extends axiallybeyond the sleeve 132 and out of the flow circulation area F. Statedotherwise, the end 24 g of the heater rod 24 b extends axially, relativeto the axis A, beyond the igniter liner aperture 16 c and into thecombustion chamber 16 b. Stated otherwise, the end 24 g traverses aprojection of the combustor liner 16 a to reach the combustion chamber.

In the embodiment shown, the end 24 g of the heater rod 24 b is locatedinside the combustion chamber 16 b. That is, the end 24 g traverses aprojection 16 a′ of the combustor liner 16 a; the projectioncorresponding to where the combustion liner 16 a would be if the igniterliner aperture 16 c were not present. In the embodiment shown, a majorportion of the length of the heating section 24 h of the heater rod 24 bis located inside the combustion chamber 16 b.

In the embodiment shown, the metal portion M that is closest to theheating section 24 h is the tips 132 g of the fins 132 e. In aparticular embodiment, a distance taken along the axis A from the end 24g of the heater rod 24 g to the metal portion is less or equal to twotimes a length along the axis A of the heating section 24 h. In aparticular embodiment, the distance taken along the axis A from the end24 g of the heater rod 24 g to the metal portion is less or equal to oneand a half time the length of the heating section 24 h taken along theaxis A. In a particular embodiment, the distance taken along the axis Afrom the end 24 g of the heater rod 24 g to the metal portioncorresponds to the length of the heating section 24 h taken along theaxis A. In a particular embodiment, the distance taken along the axis Afrom the end 24 g of the heater rod 24 g to the metal portion is abouthalf the length of the heating section 24 h taken along the axis A.

Referring to FIGS. 6 and 7, another embodiment of a sleeve is generallyshown at 232. More specifically, the sleeve 232 includes fins 232 e. Thefins 232 e include each a first section 232 e ₁ that extends from thebase 232 f toward the tip 232 g and a second section 232 e ₂ thatextends from the tip 232 g toward the base 232 f. In the embodimentshown, a length of the second sections 232 e ₂ of the fins 232 e alongthe axis A is about one and a half times the diameter D1 of the heaterrod 24 b. The second sections 232 e ₂ of the fins 232 e of the sleeve232 are grouped in groups 232 h of fins 232 e that are circumferentiallyspaced around the axis A. In the embodiment shown, the sleeve 232includes four groups 232 h of fins 232 e; each group 232 h includingthree fins 232 e for a total of twelve fins. Other configurations arecontemplated without departing from the scope of the present disclosure.For each of the groups 232 h, the fins 232 e extend radially from a wall232 i to the outer surface 232 a of the sleeve 232. The wall 232 iextends annularly around a portion of a circumference of the sleeve 232.The flow circulation area extends from the heater rod 24 b to the outersurface 232 a via spacing S2′ between each two consecutive ones of thegroups 232 h of fins 232 e.

Referring now to FIG. 8, another embodiment of a sleeve is generallyshown at 332. The sleeve 332 is similar to the sleeve depicted in FIG.6, but includes twelve fins 332 e instead of eight. Moreover, the end 24g of the glow plug 24 heater rod axially registers with a plane Pcontaining the tips 332 g of the fins 332 e. In the embodiment shown,the end 24 g of the heater rod 24 b is axially aligned, relative to theaxis A, with the igniter liner aperture 16 c. Stated otherwise, the end24 g is intersected by a projection of the combustor liner 16 a.

In the embodiment shown, the metal portion M that is closest to theheating section 24 h is the tips 332 g of the fins 332 e. In theembodiment shown, a distance taken along the axis A from the end 24 g ofthe heater rod 24 g to the metal portion is zero. In a particularembodiment, the distance is less or equal to two times a length alongthe axis A of the heating section 24 h. In a particular embodiment, thedistance taken along the axis A from the end 24 g of the heater rod 24 gto the metal portion is less or equal to one and a half time the lengthof the heating section 24 h taken along the axis A. In a particularembodiment, the distance taken along the axis A from the end 24 g of theheater rod 24 g to the metal portion corresponds to the length of theheating section 24 h taken along the axis A. In a particular embodiment,the distance taken along the axis A from the end 24 g of the heater rod24 g to the metal portion is about half the length of the heatingsection 24 h taken along the axis A.

In the embodiment shown, the end 24 g of the heater rod 24 b is axiallyaligned relative to the axis A with the projection 16 a′ of the igniterliner aperture 16 a.

Referring now to FIG. 9, another embodiment of a sleeve is generallyshown at 432. The sleeve inner surface 432 b at the flow circulationarea has a frustoconical shape with a diameter that decreases from itsdistal end 432 c to the constricted area C. As shown, the diameterdecreases linearly from the distal end 432 c of the sleeve 432 to theconstricted area C. In the embodiment shown, the end 24 g of the glowplug heater rods 24 b protrudes axially beyond the sleeve 432.

In the embodiment shown, the inner surface 432 b of the sleeve 432defines a Venturi. More specifically, the inner surface 432 b of thesleeve 432 defines a conduit having a cross-sectional areal taken alonga plane normally intersected by the axis A that increases from theconstriction C to a distal end 432 c of the sleeve 432.

It is understood that different combinations of features describedhereinare possible in alternate embodiments.

In a particular embodiment, the constricted area C brings liquid fuel,which is on the inner surface 32 b of the sleeve 32, closer to the hotpart of the heater rod 24 b, thereby encouraging vaporization, ignition,and further vaporization and combustion. In a particular embodiment, thepresence of a small gap and cavity behind the constricted area Ccollects liquid fuel prior to ignition, which is then vaporized afterignition. This vaporization might push the fuel and vapor towards thehot part of the glow plug heater rod 24 b where it ignites. This mightresult in a jet of flame that might help to ignite a fuel spray from thefuel injectors 22. In a particular embodiment, this results insuccessful flame propagation and engine light-up.

The embodiments described herein include various means of collectingliquid fuel that can then be vaporized, either by the heat of the glowplug itself, or by the heat released following initial ignition.

In the embodiment shown, the metal portion M that is closest to theheating section 24 h is the constriction C defined by the inner surface432 b of the sleeve 432. In a particular embodiment, a distance takenalong the axis A from the end 24 g of the heater rod 24 g to the metalportion is less or equal to two times a length along the axis A of theheating section 24 h. In a particular embodiment, the distance takenalong the axis A from the end 24 g of the heater rod 24 g to the metalportion is less or equal to one and a half time the length of theheating section 24 h taken along the axis A. In a particular embodiment,the distance taken along the axis A from the end 24 g of the heater rod24 g to the metal portion corresponds to the length of the heatingsection 24 h taken along the axis A. In a particular embodiment, thedistance taken along the axis A from the end 24 g of the heater rod 24 gto the metal portion is about half the length of the heating section 24h taken along the axis A.

Referring now to FIG. 10, another embodiment of a sleeve is generallyshown at 532. The sleeve 532 defines an annular plate 534 that facesaxially toward the end 24 g of the heater rod 24 b that extendscircumferentially around the heater rod 24 b in this embodiment. In theembodiment shown, the sleeve 534 is recessed relative to the combustorliner 16 a such as to define a fuel collector 536 that is delimited bythe annular plate 534 and a peripheral wall 16 c′ of the igniter lineraperture 16 c. The fuel collector 536 is configured for collecting fuelto be ignited by the heater rod 24 b. The fuel collector 536 may have afrustoconical shape. The fuel collector 536 forming a pool 536′ forreceiving fuel. The peripheral wall 16 c′ may extend circumferentiallyabout a full circumference of the heater rod 24 b. The peripheral wall16 c′ may have a frustoconical shape. The peripheral wall 16 c′ mayextend axially beyond the rod end 24 g. In a particular embodiment, theperipheral wall may be defined by the adaptor.

Referring now to FIG. 11, another embodiment of a sleeve is generallyshown at 632. The sleeve 632 corresponds to the sleeve 532 of FIG. 10but further includes an annular wall 636 that is connected to aperiphery of the annular plate 534. The annular wall 636 extendscircumferentially around the heater rod 24 b in this embodiment. In theembodiment shown, the fuel collector 638 is delimited by the annularplate 534 and the annular wall 636. The fuel collector 638 is configuredfor collecting fuel to be ignited by the heater rod 24 b. In oneembodiment, the fuel collector can extend around a full circumference ofthe heater rod, continuously or intermittently, whereas in otherembodiments, the fuel collector can extend only in one or more portions,or angular segment, of the full circumference of the heater rod.

Referring now to FIG. 12, another embodiment of a sleeve is generallyshown at 732. The sleeve 632 corresponds to the sleeve 532 of FIG. 10but slots 736 are defined in the annular plate 534. The slots 736 areconfigured for receiving therein fuel to be ignited by the heater rod 24b. Stated otherwise, the slots 736 act as fuel collectors.

Referring now to FIG. 13, another embodiment of a sleeve is generallyshown at 832. In the embodiment shown, the sleeve 832 has ridges 834 atthe inner surface 832 b. A channel 836 is located between two adjacentones of the ridges 834. The channels 836 act as fuel collectors forcontaining fuel to be ignited by the heater rod 24 b. As shown, thechannels 836 surround the heating section 24 h. The pocket may includethe channels; the channels being axially distributed.

The sleeve includes pockets 836 a defined by the channel 836. Thepockets 836 a have a radial depth that extends radially relative to theaxis A from a bottom of the channels 836 to an apex of the ridges 834.In one embodiment, the pocket can extend around a full circumference ofthe heater rod, continuously or intermittently, whereas in otherembodiments, the pocket can extend only in one or more portions, orangular segment, of the full circumference of the heater rod. The pocketmay be defined between threads defined by the inner surface of thesleeve. The pocket may extend around a full circumference of the innersurface of the sleeve.

Referring now to FIG. 14, another embodiment of a sleeve is generallyshown at 932. In the embodiment shown, the sleeve 932 circumferentiallyextends at least partially around a portion of the heating section 24 hof the heater rod 24 b. Herein, the expression “at least partiallyaround” means that the sleeve is present a plurality of circumferentiallocations distributed all around the heating section, but the sleeve 932need not continuously extend all around a full circumference about theaxis A. Herein, the expression “a portion of the heating section 24 h”means a portion taken along the axis A. In a particular embodiment, theportion of the heating section 24 h includes at least half of a totallength of the heating section 24 h taken along the axis A. A porousmedium, also referred to as a structure having open porosity, 934 isreceived within the sleeve 932 and extends radially between the heaterrod 24 b and the inner surface 932 b of the sleeve 932 and at leastpartially circumferentially around the heater rod 24 b. The porousmedium 934 may be metal foam, a porous ceramic such as a ceramic sponge,a 3D printed lattice or any structure known in the art that definesporosities in which fuel may be received. The porous medium 934 is astructure having open porosities. In one embodiment, the structurehaving open porosity can extend around a full circumference of theheater rod, continuously or intermittently, whereas in otherembodiments, the structure having open porosity can extend only in oneor more portions, or angular segment, of the full circumference of theheater rod. In a particular embodiment, the foam is radially spacedapart from the heater rod 24 b by a gap. The gap may extend around afull circumference of the heater rod 24 b or around a portion of saidcircumference. This might allow the foam to expand when exposed to hotgas. In a particular embodiment, the structure having open porosity hasan axial end being distal from the base; the axial end of the structuresloping inwardly and axially towards the base. The structure having openporosity may have a plurality of radially extending slots forming afluid circulation area around the heating section of the heater rod. Thefoam need not be axisymmetric. In a particular embodiment, the structurehaving open porosity may form part of the liner. In other words, thestructure having open porosity may be secured to the collar 16 d.

In the embodiment shown, the porous medium defines an annular surface934 a that circumferentially extends around the heater rod 24 b. In theembodiment the annular surface is angled such that as to face theheating section 24 h of the heater rod 24 b. Stated otherwise, theannular surface 934 a is an axial end that is distal from the glow plugbody 24 a; the axial end of the porous medium 934 sloping radiallyinwardly and axially towards the heater rod 24 b relative to the axis A.This can offer a greater surface area to be heated by the heatingsection 24 h compared to a configuration in which the annular surface934 a is perpendicular to the axis A.

In the embodiment shown, the porous medium 934 is connected to the innersurface 932 b of the sleeve 932. Alternatively, the porous medium 934may be connected to an end wall 932 c of the sleeve 932; the end 24 g ofthe heater rod 24 protruding axially beyond the end wall 932 c. Theporous medium 934 may be in abutment against the heating section 24 h ofthe heater rod 24 b.

It is understood that the porous medium needs not to circumferentiallyextend around a full circumference of the sleeve 932. For instance, theporous medium 932 may fill the spacing S2 (FIG. 5) located between twoadjacent fins 132 e (FIG. 5) of the sleeve 132 of FIG. 5. In otherwords, there is presence of the porous medium at a plurality ofcircumferential locations around the axis A but the porous medium neednot circumferentially extends along a full circumference. In aparticular embodiment, sections of the circumference of the innersurface of the sleeve where the porous medium is present amount to atleast half of a full circumference of said inner surface.

In the embodiment shown, the metal portion M that is closest to theheating section 24 h is on the porous medium 934. More specifically, thecloses metal portion is located on the annular surface 934 a of theporous medium 934 and at a radially inward-most point on said surface934 a. In a particular embodiment, a distance taken along the axis Afrom the end 24 g of the heater rod 24 g to the metal portion is less orequal to two times a length along the axis A of the heating section 24h. In a particular embodiment, the distance taken along the axis A fromthe end 24 g of the heater rod 24 g to the metal portion is less orequal to one and a half time the length of the heating section 24 htaken along the axis A. In a particular embodiment, the distance takenalong the axis A from the end 24 g of the heater rod 24 g to the metalportion corresponds to the length of the heating section 24 h takenalong the axis A. In a particular embodiment, the distance taken alongthe axis A from the end 24 g of the heater rod 24 g to the metal portionis about half the length of the heating section 24 h taken along theaxis A.

In one embodiment, the sleeve can be designed to extendcircumferentially around the heater rod, and radially between the heaterrod and the aperture in the combustion chamber liner, essentially actingas a plug to limit or prevent the passage of compressed air between theheater rod and the combustion chamber liner. In some embodiments,especially if the sleeve is structurally connected to a base of theigniter, a small radial gap will nonetheless be left between thecombustion chamber liner and the sleeve to facilitate insertion of thesleeve in the combustion chamber liner, but it may be preferred tootherwise minimize this radial gap. In one embodiment, the combustorliner plug extends continuously around the entire circumference of theheater rod.

The combustor liner plug extends circumferentially around the heater rod24 b. The combustor liner plug is sized and configured to extend insidethe combustor liner aperture of the gas turbine engine when the base Bis connected to the casing 25 between the heater rod 24 b and aperiphery of the aperture 25 a. The combustor liner plug forms part ofthe sleeve which is structurally connected to the base B and protrudesalong the axis A from the base B towards the rod end 24 g; the combustorliner plug being at an end of the sleeve remote from the base. Thecombustor liner plug may have a portion connected to the heater rod.

Referring now to FIG. 15, the porous medium 1034 has a radial thicknessrelative to the axis A that is less than that of the porous medium 934of FIG. 14 such that an annular spacing 1036 is created radially betweenthe heating section 24 h of the heater rod 24 b and the porous medium1034. This annular spacing 1036 might allow fuel to circulate betweenthe porous medium 1034 and the heater rod 24 b and offers a greatersurface through which the fuel may be able to penetrate the porousmedium 1034.

Referring now FIG. 16, another embodiment of a sleeve is generally shownat 1132. The sleeve 1132 is similar to the sleeve 932 of FIGS. 14 and15, but the end wall 932 c is axially offset from the porous medium 934.This might allow the fuel to circulate through the porous medium 934 inan axial direction relative to the axis A to reach a portion of theheater rod 24 b that is behind the porous medium 934.

Referring now to FIGS. 17 and 18, in the embodiment shown, the adaptor30 defines an inlet 30 m′ provided in the form of slots 30 m extendingexternally to the adaptor 30 and thereacross into the ventilation path42. The inlet 30 m′ is fluidly connected to the spacing S1. The slots 30m are located axially between the proximal end of the sleeve 1132 andthe constriction C. A swirler 40 is received in the portion of thecavity 30 i that is free of the sleeve. The annular gap G around theheater rod 24 b forms a ventilation path 42 that extendscircumferentially around the heater rod 24 b and is located radiallybetween the swirler and the adaptor 30. The ventilation path 42 extendsaxially along at least a portion of the heater rod 24 b. In oneembodiment, the ventilation path extends around the entire circumferenceof the heater rod, in a manner to cool the heater rod in a relativelyuniform manner. The swirler has an annular wall 40 a and a plurality ofhelical vanes 40 b that extend from the annular wall 40 a toward acenter of the annular wall 40 a. The helical vanes 40 b extend both inthe axial and circumferential directions relative to the axis A suchthat they wrap around the axis A. Spacing 40 c are defined between thehelical vanes 40 b, which are configured to impart a circumferentialcomponent to a flow circulating there between.

The ventilation path 42 extends from an inlet 42 a to an outlet 42 b.The inlet 42 a is fluidly connectable to the spacing S1 between theengine casing 25 and the combustor liner 16 a. The outlet 42 b extendscircumferentially around the glow plug heater rod 24 b and orientedaxially relative to the axis A. The outlet is fluidly connectable to thecombustion chamber. The ventilation path 42 may extend through the gapG. The ventilation path 42 may extend axially along a portion of theheater rod located between the heating section and the base. The inlet42 a of the ventilation path 42 may be connected to the outlet 42 b viathe constriction C. The ventilation path 42 may extend through a secondbroadening section 432 b ₂ located upstream of the constriction Crelative to the flow circulating in the ventilation path 42. Theventilation path 42 may extend through the second broadening section,the constriction, and the broadening section.

In a particular embodiment, a tip portion of the sleeve is made of adifferent material having a higher resistance to heat than a remainderof the sleeve.

The inlet 42 a of the ventilation path 42 may be extending radiallythrough the sleeve. Gas may be drawn across this ventilation path 42 viaa difference of pressure between the compressed gas path (e.g., spacingS1) and the combustion chamber during normal operation.

In a particular embodiment, the ventilation path has an inlet segmentwhich connects the compressed gas path with a gap between the sleeve andthe heater rod, that gap may act as a second segment, and may broadenbefore reaching the heating section. This might reduce the likelihood ofblowing out the flame. Alternately, the ventilation path 42 may exitacross the sleeve. The ventilation path 42 may extend along the metal toceramic junction J.

In a particular embodiment, the ventilation path may be formed withinthe sleeve and extend axially along a distal end portion of the sleeve.The sleeve may define a plurality of circumferentially interspacedconduits. The circumferential conduits may each extend along a portionof a circumference to induce a swirl in the air, to create a vortex.This might create a broadening flow. In a particular embodiment, aventilation path may be created to blow fuel upward.

More specifically, the slots 30 m are fluidly connected to theventilation path 42, which is fluidly connected to the spacing 40 cbetween the helical vanes 40 b, which are fluidly connected to the flowcirculation area F. The slots 30 m receives compressed air from thespacing S1 between the engine casing 25 and the combustor liner 16 a.The compressed air is directed along the axis A away from the end 24 gof the heater rod 24 b. Then, the compressed air flows radially to reachthe spacing 40 c and flows along and around the axis A toward the end 24g.

In the embodiment shown, the inner surface 432 b of the sleeve 432defines a convergent-divergent nozzle. More specifically, the innersurface 432 b of the sleeve 432 defines a broadening section 432 b 1.The cross-sectional area of the ventilation path 42 at the broadeningsection 432 b 1 increases past the constricted area C to decrease avelocity of the compressed air. This might reduce the cooling of theheater rod 24 b in comparison to a configuration that does not presentthe increase in the cross-sectional area. In a particular embodiment,the swirler 40 increases a cooling capability of the compressed airaround the intermediate section 24 d of the glow plug body 24 a. In aparticular embodiment, the increase in the cross-sectional area of theinner surface 432 b of the sleeve 432 decreases a cooling capability ofthe cooling air around the heating section 24 h of the heater rod 24 b.

In the embodiment shown, the swirler 40 has alignment features 40 d′provided in the form of pins 40 d extending axially relative to the axisA and being secured to the wall 40 a. The pins 40 d are slidinglyreceived within corresponding aperture 30 n of the adaptor 30 foravoiding the swirler 40 to rotate relative to the axis A. Statedotherwise, the pins maintain a circumferential alignment of the swirlerwith respect to the adaptor 30.

In a particular embodiment, the swirler may be located radially betweenthe heating section 24 h of the heater rod 24 b and the sleeve 432relative to the axis A; the swirler being axially aligned with theheating section 24 h relative to the axis A. In such a case, the sleeve432 may define apertures locate axially above the heating section 24 hto allow the compressed air to circulate within the sleeve 432 anddownwardly toward the end 24 g of the heater rod 24 b via the spacingbetween the vanes of the swirler 40.

In a particular embodiment, the compressed air that flows along theventilation path 42 may be used to cool down the sleeve at locationsproximate sensitive parts of the glow plug 24.

Referring now to FIG. 19, a glow plug in accordance with anotherembodiment is generally shown at 124. The glow plug 124 includes a body124 a and a heater rod 124 b. The glow plug body 124 a is configured tobe directly connected to the igniter aperture 25 a of the engine casing25 using threads.

In the embodiment shown, a sleeve 1232 is connected to the heater rod 24b. The sleeve 1232 is provided in the form of a ring thatcircumferentially extends around a full circumference of the heater rod24 b. The sleeve 1232 has an outer surface 1232 a that is configured tobe in abutment with the peripheral wall of the combustor liner aperture16 c of the combustor liner 16 a. An inner surface 1232 b of the sleeve1232 is in abutment with the heater rod 24. In the embodiment shown, thecooperation of the combustor liner 16 a, the sleeve 1232, and the heaterrod 24 b creates a sealing connection that prevents the combustion gasesfrom leaking from the igniter liner aperture 16 c toward the spacing S1.In other words, the sleeve 1232 fills a gap that would otherwise bepresent between the heater rod 24 b and the combustor liner 16 a. It isunderstood that the sleeve 1232 may abut either one of an inner or outersurface of the combustor liner 16 a.

In a particular embodiment, the sleeve 1232 may define fins, may containa porous medium, may define a cavity to act as a fuel collector. In aparticular embodiment, the sleeve 1232 may be defined by the heater rod24 b. The sleeve 1232 may be connected to the heater rod 24 b by beingheat shrunk there on. Any other methods of fastening the sleeve 1232 tothe heater rod 24 b known in the art may be used without departing fromthe scope of the present disclosure.

In the embodiment shown, the metal portion M that is closest to theheating section 24 h is a face of the sleeve 1232 that faces away fromthe body 124 a. In a particular embodiment, a distance taken along theaxis A from the end 24 g of the heater rod 24 g to the metal portion isless or equal to two times a length along the axis A of the heatingsection 24 h. In a particular embodiment, the distance taken along theaxis A from the end 24 g of the heater rod 24 g to the metal portion isless or equal to one and a half time the length of the heating section24 h taken along the axis A. In a particular embodiment, the distancetaken along the axis A from the end 24 g of the heater rod 24 g to themetal portion corresponds to the length of the heating section 24 htaken along the axis A. In a particular embodiment, the distance takenalong the axis A from the end 24 g of the heater rod 24 g to the metalportion is about half the length of the heating section 24 h taken alongthe axis A.

Referring now to FIG. 20, the combustor liner 16 a may define a gap 16 dfor allowing compressed air from flowing along an inner surface of thecombustor liner 16 a. The compressed air is used to cool the combustorliner 16 a via film cooling. However, the film of air created therebymight impede the ability of the heater section 24 h of the heater rod 24b to ignite the mixture of air and oil.

In the embodiment shown, the sleeve 1332 is a flow impeding member 1332′and includes an annular wall 1332 j that circumferentially extendsaround the heater rod 24 b to shield the heater rod form the film ofcooling air. More specifically, the annular wall 1332 j encloses aplenum 1332 k that is fluidly connected to the combustion chamber 16 aand in which a velocity of the fluid circulating therein is less thanthat in a remainder of the combustion chamber 16 b. The flow impedingmember 1332′ may extend along the axis A and have a distal end spacedfrom the base B and extending axially relative to the axis A beyond therod end 24 g. The flow impeding member 1332′ may be sized and configuredsuch that the distal end extends into a combustion chamber of the gasturbine engine upon the base connected to the casing 25. In a particularembodiment, the flow impeding member extends around at least haft of acircumference around the glow plug heater rod 24 b. The flow impedingmember 1332′ may be structurally connected to the base B and mayprotrude along the axis A from the base toward the rod end 24 g. Theflow impeding member 1332′ may have a portion connected to the heaterrod 24 b between the rod end 24 g and the base B. The flow impedingmember 1332′ may have a portion connected to the glow plug heater rod 24b between the rod end 24 g and the base B.

Indeed, the combustor liner can be provided with cooling aperturesdesigned to provide a curtain of cooling air along the inner surface ofthe combustor liner. The sleeve can have an annular wall which protrudesinwardly from the combustor liner and shields the heater rod from such acurtain of cooling air. In one embodiment, the protruding sleeve portioncan extend around a full circumference of the heater rod, continuously,whereas in other embodiments, the protruding sleeve can extend only inone or more portions, or angular segments, of the full circumference ofthe heater rod. This can be the case, for instance, in a situation wherethe orientation of the igniter in its socket will be known beforehand,in which case it can be preferred to use a protruding sleeve portiononly between the heater rod and the source of the curtain of coolingair, for instance.

In the embodiment shown, the sleeve 1332 has a flat end 1332 p thatdefines a annular wall circumferentially extending around the heater rod24 b; the annular wall being normal to the axis A. Having such a flatend 1332 p might allow the sleeve 1332 to contain more fuel than aconfiguration where the end 1332 p is sloped.

Referring now to FIG. 21, a glow plug in accordance with anotherembodiment is generally shown at 224. The glow plug 224 has a body 224 aand a heater rod 224 b protruding from the body 224 a. The heater rod224 b has a section 224 j located between the heating section 224 h andthe body 224 a. The section 224 j is configured to block the igniterliner aperture 16 c to impede the combustion gases from flowing out ofthe combustion chamber 16 b in the spacing S1. The body 224 a may befastened to the igniter aperture peripheral wall 25 a′ via correspondingthreads defined by the body 224 a.

In the embodiment shown, a blocking member BM is provided. The blockingmember BM extends across the igniter aperture 25 a and is configured toblock fluid communication across the igniter aperture 25 a. The blockingmember BM may be used to fluidly disconnect the igniter from a fuelsource (e.g., fuel tank) such that no fuel is injected around theheating rod 224 b.

Referring now to FIG. 22, a coil element 50 may be received within thesleeve 32. The coil element 50 may be in contact with the heater rod 24b. The coil element 50 wraps around the heater rod 24 b and extendsradially from the heater rod 24 b to the inner surface 32 b of thesleeve 32. In other words, by wrapping around, the coil element 50extends both in a circumferential direction and a radial directionrelative to the axis A. A plurality of gaps 50 a are defined betweenportions of the coil element 50 and are configured for receiving thereinfuel. The heater rod 24 b transfers its heat to the coil element 50thereby increasing a surface area being heated. This might help inigniting the mixture of fuel and air. As shown more clearly on FIG. 22a, a radial depth relative to the axis A of the coil element 50corresponds to a depth of the sleeve 32 relative to the axis A.

Referring now to FIG. 23, a coil structure 60 may be received within thesleeve 32. The coil structure 60 includes ribs 60 a that extends fromthe heater rod 24 b to the inner surface 32 b of the sleeve 32. Coilelements 60 b are each provided in an annular form and circumferentiallyextends around a full circumference of the heater rod 24 b. The coilelements 60 b are connected to the ribs 60 a. The coil elements 60 b areradially interspaced between the heater rod 24 b and the sleeve 32 anddefine gaps 60 c radially therebetween relative to the axis A. The gaps60 c are configured for receiving therein fuel. The heater rod 24 btransfers its heat to the coil elements 60 b thereby increasing asurface area being heated. This might help in igniting the mixture offuel and air. As shown more clearly on FIG. 23a , a radial depthrelative to the axis A of the coil structure 60 corresponds to a depthof the sleeve 32 relative to the axis A.

Referring now to FIG. 24, an igniter 300 in accordance with a particularembodiment is shown. The igniter 300 includes a base (not shown) and aconductor 300 a extending along an axis A from the base to an end 300 b.A heating element 300 c is electrically connected to the end 300 c ofthe conductor 300 a. An outer casing 300 d circumferentially extendsaround the conductor 300 a. The outer casing 300 c is in heat exchangerelationship with the heating element 300 c and radially spaced apartfrom the conductor 300 a by a gap 300 e. The gap 300 e is filled with aninsulator. In the embodiment shown, electricity is routed from a powersource (e.g., battery) to the heating element 300 c via the conductor300 a and is directed from the heating element 300 c back to the powersource via the outer casing 300 d. The power source may be a source ofdirect current. The heating element 300 c may be a ceramic. The heatingelement 300 c may provide for a greater surface area that becomesincandescent than that of a tip of a conventional glow plug. In aparticular embodiment, the electricity may be carried back and forthfrom the power source via the conductor 300 a.

In a particular embodiment, the conductor is made of copper. The heatingelement may be a conductive ceramic heating element. The housing may bein contact with the heating element. The heating element has a surface300 f facing away from the conductor. The surface may define a pattern.The pattern may be, for instance, grooves, and/or ridges that mightincrease the surface area in contact with the fuel. The heating elementmay be porous. In such a design, the heating element can be lessvulnerable to damage than if the heating element were exposed.

In a particular embodiment, the disclosed igniter 300 allows for agreater surface area for a same power compared to the igniter 24disclosed above. The increased surface area might improve theprobability of igniting fuel/air mixtures by hot surface ignition. Theheated surface may be wider than the igniter 24 disclosed above. Thismight allow the fuel/air mixture in the middle of the heated surface toreach the temperature needed to ignite. The ceramic might improve thelife of the adapter by protecting the metal adapter. It might bepossible to use a less expensive metal for the housing since the ceramicmight protect the tip.

In a particular embodiment, the fins 132 e, the porous medium 934, andthe ridges/channels 834, 836 may increase a surface area that is heated.In other words, without the fins, the porous medium, or the ridges, onlythe heating section 24 h of the heater rod 24 b would be heated. Bysurrounding the heating section 24 h by the fins, the porous medium, orthe channels, heat is transferred by conduction and/or radiation fromthe heating section 24 h to the fins, the porous medium, or thechannels. Having more heated surface area might help in igniting themixture of air and fuel.

In a particular embodiment, the sleeve 32 acts as a collector to collectfuel prior to be ignited by the glow plug 24. In a particularembodiment, the sleeve 32 provides a plenum around the heater rod 24 b;a velocity within the plenum being less than that outside the plenum.Such a plenum might help in igniting the mixture of air and fuel thatenters the plenum. Moreover, by having a velocity of the mixture insidethe plenum that is lower than that outside the plenum might avoidcooling the heating section 24 h, which would impair the ability of theheating section 24 h to ignite the mixture. The sleeve 32 may thereforeact as a flame stabilizer.

Referring now to FIGS. 25 and 26, there is disclosed an igniterincluding a heat spreader 1400 extending circumferentially around theglow plug heater rod 24 b. The heat spreader 1400 may be in heatexchange relationship with the glow plug heater rod 24 b for dissipatingheat generated by the glow plug heater rod 24 b. The heat spreader maybe axially aligned with the heating section 24 h of the glow plug heaterrod 24 b.

The igniter further has a housing 1402 circumferentially surrounding theglow plug heater rod 24 b. The rod end 24 g may protrude beyond thehousing 1402. The heat spreader 1400 may be secured to an end of thehousing 1402.

In the embodiment shown, the housing 1402 and the glow plug heater rod24 b are radially spaced from each other by a gap 1404 axially extendingat least along a portion of the glow plug heater rod 24 b. The gap 1404may be filled with an insulation material. In the depicted embodiment,the heat spreader circumferentially extends around a full circumferenceof the glow plug heater rod.

The heat spreader has an annular face 1400 a circumferentially extendingaround the glow plug heater rod 24 b. The annular face 1400 a may bebeveled toward the glow plug heater rod 24 b.

The heat spreader 1400 may be made of a metallic material. The heatspreader 1400 may be made of a conductive ceramic material. The heatspreader 1400 may be secured to be in contact with the glow plug heaterrod 24 b. The heat spreader 1400 may be made of Inconel™. The heatspreader 1400 may define porosities.

Referring now to FIG. 26, the heat spreader 1400 may becircumferentially surrounded by the housing 1402. More specifically, theheat spreader 1400 has an cylindrical face 1400 b that may be in contactwith the housing 1402. The housing 1402 may define a shoulder 1402 a forabutment against the heat spreader 1400.

In a particular embodiment, a catalyst may be deposited wherever fuel isexpected to accumulate and where a temperature is expected to be high.The catalyst may stay hot due to the combustion process. The catalystmay, for instance, be located on the foam, the porous media, the spiral,the ridges, the inner surface of the sleeve, etc.

In some embodiments, the igniter can be secured to the casing byfasteners, for instance, rather than torque. In such other embodimentsin particular, it can be easier to predetermine the circumferentialorientation or the igniter around its axis, when assembled. In suchcases, it can be preferred to use specifically provide the igniter withan asymmetrical design suited for the particular angular orientation.Accordingly, sleeve, flow impeding member, peripheral wall, ridges,grooves, heating element, heat spreader may be axisymmetric.

The above description is meant to be exemplary only, and one skilled inthe art will recognize that changes may be made to the embodimentsdescribed without departing from the scope of the invention disclosed.

For example, the gas turbine engine 10 has been depicted as a turbofan,but the disclosed igniters may be used in any types of gas turbineengines, such as turboprop, turboshaft, auxiliary power unit, jetturbine combined heat and power generators, jet turbine powered surfacevehicles.

Some of the igniter embodiments presented above have an axisymmetricdesign. The axisymmetricity is optional, and may be useful only in someembodiments. Some embodiments have non-axisymmetric designs. Indeed,axisymmetric designs can be particularly appropriate in a context wherethe igniter is to be secured to the gas turbine engine by a threadedengagement concentric to the heater rod axis, which is typically thecase when retrofitting the igniter to an existing spark plug aperture,because in such context, the axissymmetricity ensures that there is noneed to achieve a specific angular orientation relative to the thread.However, there are other cases where the circumferential orientation ofthe igniter relative to the socket in the gas turbine engine can beknown, such as via a specific engine design for instance, and in which anon-axisymmetric design can be preferred and better adapted to thespecific features of the environment of use. For instance, an ignitercan be designed for use in a specific orientation relative to the axisof the socket which receives it, and/or for a specific circumferentialposition (e.g. 3 O'clock, 6 O'clock) in the engine, in which specificelements of the environment, such as known position of incoming fuelmist, known position of heating air, known local orientation of gravity,etc. can be predetermined.

Embodiments disclosed herein include:

A. An igniter for a gas turbine engine comprising: a base including asecuring assembly configured to be matingly connected to a casing of thegas turbine engine, a glow plug heater rod, the glow plug heater rodextending from the base along an axis and terminating in a rod end, aflow impeding member extending along the axis and having a distal endspaced from the base and extending axially relative to the axis beyondthe rod end, the flow impeding member sized and configured such that thedistal end extends into a combustion chamber of the gas turbine engineupon the base connected to the casing.

B. A method of operating a gas turbine engine, the method comprising:circulating compressed gas in a compressed gas passage between a casingand a combustion chamber liner, the combustion chamber liner delimitinga combustion chamber, exposing a heating section of a glow plug heaterrod to a mixture of air and fuel in the combustion chamber via anaperture in the combustion chamber liner; forming a curtain of coolingair along an inner surface of said combustion chamber liner; andblocking said curtain of cooling air around an end of said glow plugheater rod, thereby providing a pocket of lower velocity around saidend.

C. A gas turbine engine comprising: a casing; a combustor liner providedinside the casing and enclosing a combustion chamber; an igniter havinga base connected to the casing, a glow plug heater rod extending fromthe base along an axis and terminating in a rod end, a flow impedingmember extending circumferentially around the heater rod along at leasta portion of a length of the glow plug heater rod, the flow impedingmember protruding axially into the combustion chamber.

Embodiments A, B, and C may include any of the following elements in anycombinations.

Element 1: the flow impeding member extends around at least half of acircumference around the glow plug heater rod. Element 2: flow impedingmember protrudes axially from the rod end. Element 3: the flow impedingmember is structurally connected to the base and protrudes along theaxis from the base towards the rod end. Element 4: the flow impedingmember has a portion connected to the glow plug heater rod between therod end and the base. Element 5: the heater rod has a heating sectionaxially extending between axially opposite ends of a heater containedwithin the glow plug heater rod, the flow impeding member extending atleast partially axially along the heater section of the heater rod.Element 6: the base includes a body of a glow plug, the glow plugincluding the heater rod and at least a casing portion of an adaptor,the casing portion of the adaptor connected to the body of the glowplug, around the body of the glow plug. Element 7: the flow impedingmember forms part of the casing portion of the adaptor. Element 8: theadaptor further comprises a liner portion, the liner portion configuredto be matingly connected to a liner of the gas turbine engine, the flowimpeding member forming part of the liner portion. Element 9: a portionof an outer surface of the base is threaded for engaging acorrespondingly threaded aperture of a casing of the gas turbine engine.Element 10: the base defines a shoulder, the shoulder defining anabutment surface that axially faces the rod end, the threaded portion ofthe base located axially between the shoulder and the rod end. Element11: the flow impeding member extends circumferentially around more thanhalf the circumference of the heater rod. Element 12: the flow impedingmember extends annularly around a full circumference of the heater rod.Element 13: a compressed gas path between the casing and the combustionchamber, further comprising at least one cooling aperture oriented todirect a curtain of air from the compressed gas path along an innersurface of said combustor liner, the sleeve protruding axially into thepath of the curtain of air to deviate the curtain of air away from theheater rod during operation. Element 14: the sleeve is connected to thebase independently of a structure of the gas turbine engine andprotrudes along the axis from the base towards the rod end. Element 15:the sleeve has a portion connected to the heater rod between gap and thebase. Element 16: the sleeve has a portion connected to the combustionchamber liner.

Still other modifications which fall within the scope of the presentinvention will be apparent to those skilled in the art, in light of areview of this disclosure, and such modifications are intended to fallwithin the appended claims.

The invention claimed is:
 1. A method of operating a gas turbine engine,the method comprising: circulating compressed gas in a compressed gaspassage between a casing and a combustion chamber liner, the combustionchamber liner delimiting a combustion chamber; exposing a heatingsection of a glow plug heater rod to a mixture of air and fuel in thecombustion chamber via an aperture in the combustion chamber liner;forming a curtain of cooling air along an inner surface of saidcombustion chamber liner, the curtain of cooling air flowing toward theglow plug heater rod; and blocking said curtain of cooling air fromimpinging upon an end of said glow plug heater rod with a flow impedingmember protruding beyond the combustion chamber liner and extending intothe combustion chamber, the flow impeding member extending through thecurtain of cooling air, thereby providing a pocket of lower velocityaround said end, the pocket extending beyond the combustion chamberliner into the combustion chamber.
 2. The method of claim 1, wherein theforming of the curtain of cooling air includes flowing compressed airthrough a film cooling aperture defined by the combustion chamber liner,the film cooling aperture defined between two overlapping sections ofthe combustion chamber liner.
 3. The method of claim 1, wherein the flowimpeding member extends around a full circumference of the glow plugheater rod.
 4. The method of claim 1, wherein the flow impeding memberextends at least partially axially along a heating section of the glowplug heater rod.
 5. A gas turbine engine comprising: a casing; acombustor liner provided inside the casing and enclosing a combustionchamber, the combustor liner defining a film cooling aperture; and anigniter having: a base connected to the casing, a glow plug heater rodextending from the base along an axis and terminating in a rod end, thefilm cooling aperture configured to direct cooling air along thecombustor liner towards the glow plug heater rod, and a flow impedingmember extending circumferentially around the glow plug heater rod alongat least a portion of a length of the glow plug heater rod, the flowimpeding member protruding beyond the combustor liner and extending intothe combustion chamber, the flow impeding member extending through acurtain of air outputted by the film cooling aperture and blocking thecooling air from impacting the glow plug heater rod.
 6. The gas turbineengine of claim 5, further comprising a compressed gas path between thecasing and the combustion chamber, the film cooling aperture in fluidflow communication with the compressed gas path, the flow impedingmember protruding axially into the path of the curtain of air to deviatethe curtain of air away from the glow plug heater rod during operation,the film cooling aperture defined between two overlapping sections ofthe combustor liner.
 7. The gas turbine engine of claim 5, wherein theflow impeding member is connected to the base and protrudes along theaxis from the base towards the rod end.
 8. The gas turbine engine ofclaim 5, wherein the flow impeding member has a portion connected to theglow plug heater rod between the rod end and the base.
 9. The gasturbine engine of claim 5, wherein the flow impeding member has aportion connected to the combustor liner.
 10. The gas turbine engine ofclaim 5, wherein the flow impeding member extends around at least halfof a circumference of the glow plug heater rod.
 11. The gas turbineengine of claim 5, wherein the flow impeding member protrudes axiallyfrom the rod end.
 12. The gas turbine engine of claim 5, wherein theflow impeding member is structurally connected to the base and protrudesalong the axis from the base towards the rod end.
 13. The gas turbineengine of claim 5, wherein the glow plug heater rod has a heatingsection axially extending between axially opposite ends of a heatercontained within the glow plug heater rod, the flow impeding memberextending at least partially axially along the heating section of theglow plug heater rod.
 14. The gas turbine engine of claim 5, wherein thebase includes a body of a glow plug, the glow plug including the glowplug heater rod and at least a casing portion of an adaptor, the casingportion of the adaptor connected to the body of the glow plug, aroundthe body of the glow plug.
 15. The gas turbine engine of claim 14,wherein the flow impeding member forms part of the casing portion of theadaptor.
 16. The gas turbine engine of claim 5, wherein the adaptorfurther comprises a liner portion, the liner portion matingly connectedto the combustor liner of the gas turbine engine, the flow impedingmember forming part of the liner portion.
 17. The gas turbine engine ofclaim 5, wherein a portion of an outer surface of the base is threadedand engaged in a threaded aperture of the casing of the gas turbineengine.
 18. The gas turbine engine of claim 17, wherein the base definesa shoulder, the shoulder defining an abutment surface that axially facesthe rod end, wherein the portion of the outer surface of the base islocated axially between the shoulder and the rod end.
 19. The gasturbine engine of claim 5, wherein the flow impeding member extendscircumferentially around more than half of a circumference of the glowplug heater rod.
 20. The gas turbine engine of claim 5, wherein the flowimpeding member extends annularly around a full circumference of theglow plug heater rod.